Heat exchanger array

ABSTRACT

A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

BACKGROUND

The present disclosure relates generally to gas turbine engines, andmore particularly to a heat exchanger array.

A gas turbine engine typically includes a high pressure spool, acombustion system, and a low pressure spool disposed within an enginecase to form a generally axial, serial flow path about the enginecenterline. The high pressure spool includes a high pressure turbine, ahigh pressure shaft extending axially forward from the high pressureturbine, and a high pressure compressor connected to a forward end ofthe high pressure shaft. The low pressure spool includes a low pressureturbine, which is disposed downstream of the high pressure turbine, alow pressure shaft, which typically extends coaxially through the highpressure shaft, and a fan connected to a forward end of the low pressureshaft, forward of the high pressure compressor. The combustion system isdisposed between the high pressure compressor and the high pressureturbine and receives compressed air from the compressors and fuelprovided by a fuel injection system. A combustion process is carried outwithin the combustion system to produce high energy gases to producethrust and turn the high and low pressure turbines, which drive thecompressor and the fan to sustain the combustion process.

The high energy gases contain a substantial amount of thermal energy,which is transferred to the high and low pressure turbines. Therefore,the high and low pressure turbines are cooled using air that is bledfrom the high pressure compressor. This cooling air can be cooled usinga heat exchanger prior to flowing to the turbines in order to maximizethe cooling capacity of the cooling air. In such an arrangement, thecooling air flows through the hot side of the heat exchanger, andanother fluid must be used for the cold side of the heat exchanger.

SUMMARY

According to one embodiment of the present invention, a heat exchangerarray includes a first row of heat exchangers with a hot side and a coldside, a second row of heat exchangers with a hot side and a cold side,and side curtains. The heat exchangers of the first row are spaced apartto define first gaps. The heat exchangers of the second row are spacedapart to define second gaps and are positioned downstream of andstaggered from the heat exchangers of the first row such that the heatexchangers of the second row are aligned with the first gaps and theheat exchangers of the first row are aligned with the second gaps. Eachof the side curtains is in close proximity to a heat exchanger in thefirst row and a heat exchanger in the second row. The side curtains arearranged to define a neck region upstream of and aligned with each heatexchanger in the first row and each heat exchanger in the second row.Each neck region has a neck area that is less than a frontal area of theheat exchanger with which it is aligned.

According to another embodiment of the present invention, a gas turbineengine includes a fan section, a compressor section downstream of thefan section, a combustor section downstream of the compressor section, afirst turbine section downstream of the combustor section, the firstturbine section being connected to the compressor section, a secondturbine section downstream of the first turbine section, the secondturbine section being connected to the fan section, and a heat exchangerarray that is fluidly connected to secondary air from the fan section.The heat exchanger array includes a first row of heat exchangers spacedapart to define first gaps, a second row of heat exchangers spaced apartto define second gaps, and side curtains. Each of the side curtains isin close proximity to one of the heat exchangers in the first row andone of the heat exchangers in the second row. The side curtains define aset of first passages and a set of second passages. In each firstpassage, secondary air flows through one of the heat exchangers in thefirst row and subsequently through one of the second gaps. In eachsecond passage, the secondary air flows through one of the first gapsand subsequently through one of the heat exchangers in the second rowheat.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic side cross-section view of an embodiment of a gasturbine engine.

FIG. 2 is a schematic side cross-section view of another embodiment ofthe gas turbine engine in FIG. 1.

FIG. 3 is a schematic cross-sectional view of one embodiment of aportion of a heat exchanger array of the gas turbine engine in FIGS. 1and 2.

FIG. 4 is a schematic cross-sectional view of another embodiment of aportion of a heat exchanger array of the gas turbine engine in FIGS. 1and 2.

DETAILED DESCRIPTION

FIG. 1 is a schematic side cross-section view of gas turbine engine 10.Although FIG. 1 depicts a turbofan gas turbine engine typically used foraircraft propulsion, the invention is readily applicable to gas turbinegenerators and other similar systems incorporating rotor-supported,shaft-driven turbines. Shown in FIG. 1 are gas turbine engine 10, fan12, gearbox 13, low pressure compressor (LPC) 14, high pressurecompressor (HPC) 16, combustor section 18, high pressure turbine (HPT)20, low pressure turbine (LPT) 22, fan case 24, LPC case 26, HPC case28, HPT case 30, LPT case 32, low pressure shaft 34, high pressure shaft36, exit guide vanes 38, injectors 40, HPT blades 41, LPT blades 42,support rotor 44, vane airfoil sections 46, nacelle 48, upperbifurcation 50U, lower bifurcation 50L, bracket 52, heat exchanger array54, bleed air flow path 56, cooled bleed air flow path 58, inlet air A,primary air A_(P), secondary air A_(S) (also known as bypass air), andlongitudinal engine centerline axis C_(L).

In the illustrated embodiment, gas turbine engine 10 comprises adual-spool turbofan engine in which the advantages of the presentinvention are particularly well illustrated. Gas turbine engine 10, ofwhich the operational principles are well known in the art, comprisesfan 12, LPC 14, HPC 16, combustor section 18, HPT 20, and LPT 22, whichare each concentrically disposed around longitudinal engine centerlineaxis C_(L). Fan 12 is enclosed at its outer diameter within fan case 24.Likewise, the other engine components are correspondingly enclosed attheir outer diameters within various engine casings, including LPC case26, HPC case 28, HPT case 30 and LPT case 32. Fan 12 and LPC 14 areconnected to LPT 22 through low pressure shaft 34, and together with fan12, LPC 14, LPT 22, and low pressure shaft 34 comprise the low pressurespool. HPC 16 is connected to HPT 20 through high pressure shaft 36, andtogether HPC 16, HPT 20, and high pressure shaft 36 comprise the highpressure spool.

Depicted in FIG. 1 is one embodiment of gas turbine engine 10, to whichthere are alternative embodiments. For example, gas turbine engine 10can be a three spool engine. In such an embodiment, gas turbine engine10 has an intermediate compressor between LPC 14 and HPC 16 and anintermediate turbine between HPT 20 and LPT 22, wherein the intermediatecompressor is connected to the intermediate turbine with an additionalshaft.

Nacelle 48 is adjacent to fan case 24 and defines a substantiallyannular duct around the core engine within LPC case 26, HPC case 28, HPTcase 30 and LPT case 32. Nacelle 48 is bifurcated with upper bifurcation50U and lower bifurcation 50L. Upper bifurcation 50U and lowerbifurcation 50L cover support elements, such as electrical lines,hydraulic lines, fuel lines, lubricant carrying lines, for the coreengine within LPC case 26, HPC case 28, HPT case 30 and LPT case 32.Upper bifurcation 50U and lower bifurcation 50L also define upper andlower bifurcation ducts, which provide space to fit additionalcomponents into gas turbine engine 10, such as heat exchanger array 54.In the embodiment shown, heat exchanger array 54 is located in lowerbifurcation 50L and is attached to the core engine with bracket 52. Inalternative embodiments, heat exchanger array 54 can be located in upperbifurcation 50U or both lower bifurcation 50L and upper bifurcation 50U.

During normal operation, inlet air A enters engine 10 where it isdivided into streams of primary air A_(P) and secondary air A_(S) afterpassing through fan 12. Fan 12 is rotated by LPT 22 through low pressureshaft 34 (either directly or through gearbox 13 as shown) to acceleratesecondary air A_(S) (also known as bypass air, such as fan air) throughexit guide vanes 38 and through nacelle 48, thereby producing a majorportion of the thrust output of engine 10. Primary air A_(P) (also knownas gas path air) is directed first into LPC 14 and then into HPC 16. LPC14 and HPC 16 work together to incrementally step up the pressure ofprimary air A_(P). HPC 16 is rotated by HPT 20 through low pressureshaft 34 to provide compressed air to combustor section 18. Thecompressed air is delivered to combustor section 18, along with fuelthrough injectors 40, such that a combustion process can be carried outto produce the high energy gases necessary to turn HPT 20 and LPT 22.Primary air A_(P) continues through gas turbine engine 10 whereby it istypically passed through an exhaust nozzle to further produce thrust.

After being compressed in LPC 14 and HPC 16 and participating in acombustion process in combustor section 18 to increase pressure andenergy, primary air A_(P) flows through HPT 20 and LPT 22 such that HPTblades 41 and LPT blades 42 extract energy from the flow of primary airA_(P). Primary air A_(P) impinges on HPT blades 41 to cause rotation ofhigh pressure shaft 36, which turns HPC 16. Primary air A_(P) alsoimpinges on LPT blades 42 to cause rotation of support rotor 44 and lowpressure shaft 34, which turns fan 12 and LPC 14.

In addition, a portion of primary air A_(P) (bleed air) can be bled offfrom at least one of LPC 14, HPC 16, and in between LPC 14 and HPC 16for use as cooling air. The bleed air is cooled in multiple heatexchangers in heat exchanger array 54 prior to being used to coolcomponents of HPT 20 and LPT 22. The bleed air travels through coolingair flow path 56 from at least one of LPC 14, HPC 16, and in between LPC14 and HPC 16 to the hot side of the heat exchangers in heat exchangerarray 54. The cold side of the heat exchangers in heat exchanger array54 receives secondary air A_(S), which is used to cool the bleed air inthe hot side of the heat exchangers in heat exchanger array 54. Thecooled bleed air leaves heat exchanger array 54 and travels to at leastone of HPT 20 and LPT 22 via cooled bleed air flow path 58 to cool thecomponents in HPT 20 and LPT 22.

It is advantageous to cool components of HPT 20 and LPT 22, because thetemperatures of the components in HPT 20 and LPT 22 would rise toexcessively high levels if left unchecked. It can also be desirable tooperate HPT 20 and LPT 22 at higher temperatures to increases the fuelefficiency of gas turbine engine 10. Cooling the bleed air in heatexchanger array 54 increases the cooling capacity of the bleed air,which allows for higher operating temperatures in HPT 20 and LPT 22while keeping the components therein within their allowable thermaloperating ranges.

FIG. 2 is a schematic side cross-section view of gas turbine engine 10′,another embodiment of gas turbine engine 10 in FIG. 1. Shown in FIG. 2are gas turbine engine 10′, fan 12, gearbox 13, low pressure compressor(LPC) 14, high pressure compressor (HPC) 16, combustor section 18, highpressure turbine (HPT) 20, low pressure turbine (LPT) 22, fan case 24,LPC case 26, HPC case 28, HPT case 30, LPT case 32, low pressure shaft34, high pressure shaft 36, exit guide vanes 38, injectors 40, HPTblades 41, LPT blades 42, support rotor 44, vane airfoil sections 46,nacelle 48, upper bifurcation 50U, lower bifurcation 50L, bracket 52,heat exchanger array 54, oil flow path 56′, cooled oil flow path 58′,inlet air A, primary air A_(P), secondary air A_(S) (also known asbypass air), and longitudinal engine centerline axis C_(L).

Gas turbine engine 10′ is structurally and functionally substantiallysimilar to gas turbine engine 10 of FIG. 1, except heat exchanger array54 is used to cool the oil in gearbox 13 instead of being used to coolcooling air. Oil from gearbox 13 travels through oil flow path 56′ tothe hot side of the heat exchangers in heat exchanger array 54. The coldside of the heat exchangers in heat exchanger array 54 receivessecondary air A_(S), which is used to cool the oil in the hot side ofthe heat exchangers in heat exchanger array 54. The cooled oil leavesheat exchanger array 54 and travels back to gearbox 13 via cooled oilflow path 58′.

FIG. 3 is a schematic cross-sectional view of a portion of heatexchanger array 54, seen in gas turbine engine 10 in FIG. 1 and gasturbine engine 10′ in FIG. 2. Heat exchanger array 54 includes first row60 with heat exchangers 60A and 60B and second row 62 with heatexchangers 62A, 62B, and 62C. Each of heat exchangers 60A-60B and62A-62C has thickness T and frontal area A_(F). In the embodiment shown,first row 60 includes two heat exchangers and second row 62 includesthree heat exchangers. In alternate embodiments, first row 60 and secondrow 62 can include any number of heat exchangers. Heat exchangers60A-60B and 62A-62C include intakes 64 and exhausts 66. Heat exchangerarray 54 also includes side curtains 68. FIG. 3 also shows stream tubeF₁, stream tube F₂, and cold fluid C.

In first row 60, heat exchangers 60A and 60B are spaced apart from oneanother by gaps G1. In second row 62, heat exchangers 62A-62C are alsospaced apart from one another by gaps G2. Additionally, heat exchangers62A-62C of second row 62 are positioned downstream of and staggered fromheat exchangers 60A-60B of first row 60 such that heat exchangers62A-62C are interleaved between heat exchangers 60A and 60B. Heatexchangers 60A-60B are aligned with gaps G2, and heat exchangers 62A-62Care aligned with gaps G1. Heat exchangers 60A-60B in first row 60 can bethe same size as heat exchangers 62A-C in second row 62. In alternativeembodiments, heat exchangers 60A-60B can be smaller or larger than heatexchangers 62A-62C. In the embodiment shown, heat exchangers 60A-60B and62A-62C are shell and tube heat exchangers. In alternative embodiments,heat exchangers 60A-60B and 62A-62C can be any type of heat exchangers,including plate fin heat exchangers and heat exchangers made by additivemanufacturing.

Each of heat exchangers 60A-60B and 62A-62C is in close proximity to apair of side curtains 68 such that a somewhat leak proof seal is formedbetween a pair of side curtains 68 and each of corresponding heatexchangers 60A-60B and 62A-62C. Side curtains 68 can be made of metallicor composite material. Heat exchangers 60A-60B and 62A-62C can beattached to side curtains 68 with fasteners such as bolts or rivets, orcan be welded to side curtains 68. Side curtains 68 define neck regionsN. Each neck region N is positioned upstream of and aligned with one ofheat exchangers 60A-60B and 62A-62C. Each neck region N has a neck areathat is less than frontal area A_(F) of each of heat exchangers 60A-60Band 62A-62C with which each neck region N is aligned.

Side curtains 68 and heat exchangers 60A-60B and 62A-62C define passagesfor cold fluid C through first row 60 and second row 62. When cold fluidC flows through each of heat exchangers 60A-60B in first row 60, coldfluid C first flows through one of neck regions N, then through one ofheat exchangers 60A or 60B, and finally through one of gaps G2. Whencold fluid C flows through each of heat exchangers 62A-62C, cold fluid Cfirst flows through one of gaps G1 and one of neck regions N prior toflowing through one of heat exchangers 62A-62C.

Heat exchanger array 54 can be used to cool a fluid, such as bleed airfrom the HPC or LPC in gas turbine engine 10 of FIG. 1, oil from gearbox13 in gas turbine engine 10′ in FIG. 2, or any other fluid that requirescooling. Heat exchangers 60A-60B and 62A-62C receive a hot fluid throughintakes 64. The hot fluid is cooled by cold fluid C passing through eachof heat exchangers 60A-60B and 62A-62C as described above. Cold fluid Ccan be secondary air A_(S) (also known as bypass air such as fan air) ingas turbine engine 10 in FIG. 1 and gas turbine engine 10′ in FIG. 2, orany other suitable fluid. The cooled fluid leaves heat exchangers60A-60B and 62A-62C through exhausts 66.

Thickness T of heat exchangers 60A-60B and 62A-62C can be relativelysmall if there is a significant difference in temperature and pressurebetween the cold side and hot side of each of heat exchangers 60A-60Band 62A-62C. For example, if the hot fluid is bleed air in gas turbineengine 10 of FIG. 1, the temperature of the hot fluid can be 1000degrees Fahrenheit (538° C.) or even higher, and the pressure of the hotfluid can be 500 psi or higher. If cold fluid C is secondary air such asfan air, the temperature can be between approximately 0 degreesFahrenheit (−18° C.) and 50 degrees Fahrenheit (10° C.), and thepressure is close to ambient pressure, or 1 psi (6891 Pascal). Thesignificant temperature difference between the cold side and hot side ofheat exchangers 60A-60B and 62A-62C causes cold fluid C to reach thesame temperature as the hot fluid very quickly as the cold fluid passesthrough heat exchangers 60A-60B and 62A-62C. Therefore, thickness T ofheat exchanger 60A-60B and 62A-62C can be optimized based on theanticipated temperature difference between cold fluid C and the hotfluid.

Heat exchanger array 54 is advantageous, because the arrangement offirst row 60 and second row 62 allows for greater heat transfer than ispossible with a single row of heat exchangers, as adding a second row ofheat exchangers increases frontal area for heat transfer. This isparticularly advantageous in the context of gas turbine engines, such asgas turbine engine 10 of FIG. 1 and gas turbine engine 10′ of FIG. 2,because there is limited space in which to fit heat exchangers in orderto provide cooled cooling air to the LPT and HPT or to cool the oil inthe gearbox.

The shape of side curtains 68 prevents turbulent flow from occurring ascold fluid C enters heat exchangers 60A-60B and 62A-62C. When cold fluidC flows towards heat exchanger 60B, for example, cold fluid Cexperiences a “blockage” due to the physical blockage created by heatexchanger 60B. Without side curtains 68, the physical blockage wouldcause stream tubes of cold fluid C to splay laterally away from heatexchanger 60B, particularly at the edges of heat exchanger B. Theresulting turbulence would cause a pressure drop, which could reduce thethrust in gas turbine engine 10 of FIG. 1, for example. Side curtains 68keep stream tubes of cold fluid C flowing in an orderly fashion as thestream tubes approach heat exchanger 60B, as represented by stream tubeF₁ in FIG. 3. Side curtains 68 also direct stream tubes past first row60 and through gaps G2 so that cold fluid C approaches second row 62without pressure losses, as represented by stream tube F₂ in FIG. 3.

When cold fluid C flows towards heat exchanger 60B, for example, coldfluid C also experiences a “blockage” due to the difference in the flowparameter of cold fluid C as it approaches heat exchanger 60B and theflow parameter within heat exchanger 60B as cold fluid C is removes heatfrom the hot side of heat exchanger 60B. Flowparameter=((w*(T{circumflex over ( )}0.5))/(A*P)), where w=mass flow,T=temperature, A=local area, and P=local pressure. The flow parameterwithin heat exchanger 60B is much less than the flow parameter of coldfluid C as it approaches heat exchanger 60B due to the significant heataddition that occurs in heat exchanger 60B. Neck N created by the shapeof side curtains 68 significantly reduces the difference in flowparameter between heat exchanger 60B and cold fluid C. The shape of sidecurtains 68 thus also allows for first row 60 and second row 62 to beequally effective in transferring heat, even though second row 62 isdownstream of first row 60, as cold fluid C enters heat exchangers62A-62C of second row 62 with almost the same pressure as cold fluid Centers heat exchangers 60A-60B of first row 60.

FIG. 4 is a schematic cross-sectional view of heat exchanger array 54′,another embodiment of heat exchanger array 54 of FIG. 3. Heat exchangerarray 54′ includes first row 60 with heat exchangers 60A and 60B andsecond row 62 with heat exchangers 62A, 62B, and 62C. Heat exchangers60A-60B and 62A-62C includes intakes 64 and exhausts 66 (shown in FIG.3). Intakes 64 and exhausts 66 are covered by fairings 70. Heatexchanger array 54′ also includes double walled side curtains 68′. Eachof heat exchangers 60A-60B and 62A-62C has a thickness T and a frontalarea A_(F). FIG. 4 also shows stream tube F₁, stream tube F₂, and coldfluid C.

Heat exchanger array 54′ is substantially similar to heat exchangerarray 54 of FIG. 3, except heat exchanger array 54′ also includes doublewalled side curtains 68′ and fairings 70. Intakes 64 and exhausts 66 cancause turbulent flow near the edges of heat exchangers 60A-60B and62A-62C. Fairings 70 cover intakes 64 and exhausts 66, which furtherprevents stream tubes of cold fluid C from splaying away from heatexchangers 60A-60B and 62A-62C and causing turbulent flow as cold fluidC approaches first row 60 and second row 62. Double walled side curtains68′ also further prevents turbulent flow, as fairings 70 can be placedinto pockets of double walled side curtains 68′ to further removeintakes 64 and exhausts 66 from the flow path of cold fluid C.

In the embodiment shown, heat exchanger array 54′ includes both fairings70 and double walled side curtains 68′. In alternate embodiments, heatexchanger array 54′ can include fairings 70 without double walled sidecurtains 68′ or double walled side curtains 68′ without fairings 70. Inanother alternate embodiment, heat exchanger array 54′ can includedouble walled side curtains with pockets for heat exchangers 60A-60B offirst row 60 without pockets for heat exchangers 62A-62C of second row62.

Discussion of Possible Embodiments

The following are non-exclusive descriptions of possible embodiments ofthe present invention.

A heat exchanger array according to an exemplary embodiment of thisinvention, among other possible things includes: a heat exchanger arraywith a first row of heat exchangers with a hot side and a cold side, asecond row of heat exchangers with a hot side and a cold side, and sidecurtains. The heat exchangers of the first row are spaced apart todefine first gaps. The heat exchangers of the second row are spacedapart to define second gaps and are positioned downstream of andstaggered from the heat exchangers of the first row such that the heatexchangers of the second row are aligned with the first gaps and theheat exchangers of the first row are aligned with the second gaps. Eachof the side curtains is in close proximity to a heat exchanger in thefirst row and a heat exchanger in the second row. The side curtains arearranged to define a neck region upstream of and aligned with each heatexchanger in the first row and each heat exchanger in the second row.Each neck region has a neck area that is less than a frontal area of theheat exchanger with which it is aligned.

The heat exchanger array of the preceding paragraph can optionallyinclude, additionally and/or alternatively, any one or more of thefollowing features, configurations and/or additional components:

A further embodiment of the foregoing heat exchanger array, wherein theheat exchanger array is located in at least one of an upper bifurcationand a lower bifurcation of a nacelle of a gas turbine engine.

A further embodiment of any of the foregoing heat exchanger arrays,wherein the hot side of each of the heat exchangers is fluidly connectedto at least one of a low pressure compressor and a high pressurecompressor and the cold side of each of the heat exchangers ispositioned to receive secondary air from a fan.

A further embodiment of any of the foregoing heat exchanger arrays,wherein the hot side of each of the plurality of heat exchangers isfluidly connected to oil from a gearbox of the gas turbine engine andthe cold side of each of the plurality of heat exchangers is positionedto receive secondary air from a fan.

A further embodiment of any of the foregoing heat exchanger arrays,wherein the side curtains are formed of metallic or composite material.

A further embodiment of any of the foregoing heat exchanger arrays,wherein the side curtains form a leak proof seal with the heatexchangers.

A further embodiment of any of the foregoing heat exchanger arrays,wherein each of the heat exchangers has a first portion with an intakecovered by a first fairing and a second portion with an exhaust coveredby a second fairing.

A further embodiment of any of the foregoing heat exchanger arrays,wherein each of the plurality of side curtains includes a first pocketfor receiving the first fairing or the second fairing of one of the heatexchangers in the first row.

A further embodiment of any of the foregoing heat exchanger arrays,wherein each of the plurality of side curtains further includes a secondpocket for receiving the first fairing or the second fairing of one ofthe heat exchangers in the second row.

A further embodiment of any of the foregoing heat exchanger arrays,wherein each of the heat exchangers is a shell and tube heat exchanger,a plate fin heat exchanger, or a heat exchanger formed by additivemanufacturing.

A gas turbine engine according to an exemplary embodiment of thisinvention, among other possible things includes: a fan section, acompressor section downstream of the fan section, a combustor sectiondownstream of the compressor section, a first turbine section downstreamof the combustor section, the first turbine section being connected tothe compressor section, a second turbine section downstream of the firstturbine section, the second turbine section being connected to the fansection, and a heat exchanger array that is fluidly connected tosecondary air from the fan section. The heat exchanger array includes afirst row of heat exchangers spaced apart to define first gaps, a secondrow of heat exchangers spaced apart to define second gaps, and sidecurtains. Each of the side curtains is in close proximity to one of theheat exchangers in the first row and one of the heat exchangers in thesecond row. The side curtains define a set of first passages and a setof second passages. In each first passage, secondary air flows throughone of the heat exchangers in the first row and subsequently through oneof the second gaps. In each second passage, the secondary air flowsthrough one of the first gaps and subsequently through one of the heatexchangers in the second row heat.

The gas turbine engine of the preceding paragraph can optionallyinclude, additionally and/or alternatively, any one or more of thefollowing features, configurations and/or additional components:

A further embodiment of the foregoing gas turbine engine, wherein theplurality of side curtains of the heat exchanger array are arranged todefine a plurality of neck regions, each neck region positioned upstreamof and aligned with one heat exchanger of the first row or one heatexchanger of the second row, wherein each neck region is narrower than afrontal area of the heat exchanger with which it is aligned.

A further embodiment of any of the foregoing gas turbine engines,wherein the heat exchanger array is located in at least one of an upperbifurcation and a lower bifurcation of a nacelle of the gas turbineengine.

A further embodiment of any of the foregoing gas turbine engines,wherein the heat exchanger array is configured to receive bleed air fromthe compressor section and configured to exhaust cooled bleed air fordelivery to at least one of the first turbine section and the secondturbine section.

A further embodiment of any of the foregoing gas turbine engines,wherein the heat exchanger array is configured to receive oil from agearbox of the gas turbine engine and configured to exhaust cooled oilfor delivery back to the gearbox.

A further embodiment of any of the foregoing gas turbine engines,wherein the side curtains of the heat exchanger array are formed of ametallic or composite material.

A further embodiment of any of the foregoing gas turbine engines,wherein the side curtains of the heat exchanger array form a leak proofseal with the heat exchangers.

A further embodiment of any of the foregoing gas turbine engines,wherein each of the heat exchangers of the heat exchanger array has afirst portion with an intake covered by a first fairing and a secondportion with an exhaust covered by a second fairing.

A further embodiment of any of the foregoing gas turbine engines,wherein each of the plurality of side curtains of the heat exchangerarray includes a first pocket for receiving the first fairing or thesecond fairing of one of the heat exchangers in the first row and asecond pocket for receiving the first fairing or the second fairing ofone of the heat exchangers in the second row.

A further embodiment of any of the foregoing gas turbine engines,wherein each of the heat exchangers in the heat exchanger array is ashell and tube heat exchanger, a plate fin heat exchanger, or a heatexchanger formed by additive manufacturing.

While the invention has been described with reference to an exemplaryembodiment(s), it will be understood by those skilled in the art thatvarious changes may be made and equivalents may be substituted forelements thereof without departing from the scope of the invention. Inaddition, many modifications may be made to adapt a particular situationor material to the teachings of the invention without departing from theessential scope thereof. Therefore, it is intended that the inventionnot be limited to the particular embodiment(s) disclosed, but that theinvention will include all embodiments falling within the scope of theappended claims.

The invention claimed is:
 1. A heat exchanger array comprising: a firstrow of heat exchangers with a hot side and a cold side wherein the heatexchangers of the first row are spaced apart to define first gaps; asecond row of heat exchangers with a hot side and a cold side, whereinthe heat exchangers of the second row are spaced apart, to define secondgaps and are positioned downstream of and staggered from the heatexchangers of the first row such that the heat exchangers of the secondrow are aligned with the first gaps and the heat exchangers of the firstrow are aligned with the second gaps; and a plurality of side curtains,each of the plurality of side curtains in close proximity to one of theheat exchangers in the first row and one of the heat exchangers in thesecond row; wherein the plurality of side curtains are arranged todefine a first plurality of neck regions and a second plurality of neckregions, each neck region of the first plurality of neck regions beingpositioned upstream of and aligned with one heat exchanger of the firstrow of heat exchangers, and each neck region of the second plurality ofneck regions being positioned upstream of and aligned with one heatexchanger of the second row of heat exchangers; wherein each heatexchanger is aligned with a neck region of the first plurality of neckregions or the second plurality of neck regions and each neck region hasa neck area that is less than a frontal area of the heat exchanger withwhich it is aligned such that the side curtains prevent turbulent flowfrom occurring as cold fluid enters the heat exchangers of the first rowand the heat exchangers of the second row and the side curtains reduce adifference in flow parameter between the cold fluid and each heatexchanger; wherein the plurality of side curtains define a set of firstpassages in each of which the cold fluid flows through one of the neckregions of the first plurality of neck regions, then through thecorresponding heat exchanger of the first row of heat exchangers, andsubsequently through the corresponding second gap of the second gaps;wherein the plurality of side curtains define a set of second passagesin each of which the cold fluid flows through one of the first gaps andthe corresponding neck region of the second plurality of neck regions,and subsequently through the corresponding heat exchanger of the secondrow of heat exchangers; and wherein each of the heat exchangers of thefirst row and each of the heat exchangers of the second row have a firstportion with an intake and a second portion with an exhaust, and each ofthe plurality of side curtains is double walled to form a first pockettherewithin for receiving the intake or the exhaust of one of the heatexchangers of the first row and a second pocket therewithin forreceiving the intake or exhaust of one of the heat exchangers of thesecond row.
 2. The heat exchanger array of claim 1 wherein the heatexchanger array is positioned within a turbofan gas turbine engine. 3.The heat exchanger array of claim 2, wherein the heat exchanger array islocated in at least one of an upper bifurcation and a lower bifurcationof a nacelle of the gas turbine engine.
 4. The heat exchanger array ofclaim 3, wherein the hot side of each of the heat exchangers is fluidlyconnected to at least one of a low pressure compressor and a highpressure compressor and the cold side of each of the heat exchangers ispositioned to receive the cold fluid which is a bypass air from a fan.5. The heat exchanger array of claim 3, wherein the hot side of each ofthe plurality of heat exchangers is fluidly connected to oil from agearbox of the gas turbine engine and the cold side of each of theplurality of heat exchangers is positioned to receive the cold fluidwhich is a bypass air from a fan.
 6. The heat exchanger array of claim1, wherein the plurality of side curtains are formed of metallic orcomposite material.
 7. The heat exchanger array of claim 1, wherein eachof the first portions is covered by a first fairing and each of thesecond portions is covered by a second fairing.
 8. The heat exchangerarray of claim 7, wherein each of the first pockets receives the firstfairing or the second fairing of the corresponding one of the heatexchangers of the first row.
 9. The heat exchanger array of claim 8,wherein each of the second pockets receives the first fairing or thesecond fairing of the corresponding one of the heat exchangers of thesecond row.
 10. The heat exchanger array of claim 1, wherein each of theheat exchangers is a shell and tube heat exchanger, a plate fin heatexchanger, or a heat exchanger formed by additive manufacturing.
 11. Agas turbine engine comprising: a fan section; a compressor sectiondownstream of the fan section; a combustor section downstream of thecompressor section; a first turbine section downstream of the combustorsection, the first turbine section being connected to the compressorsection; a second turbine section downstream of the first turbinesection, the second turbine section being connected to the fan section;and a heat exchanger array that is fluidly connected to bypass air fromthe fan section the heat exchanger array comprising: a first row of heatexchangers spaced apart to define first gaps; a second row of heatexchangers spaced apart to define second gaps; and a plurality of sidecurtains, each of the plurality of side curtains in close proximity toone of the heat exchangers in the first row and one of the heatexchangers in the second row; wherein the plurality of side curtains arearranged to define a first plurality of neck regions and a secondplurality of neck regions, each neck region of the first plurality ofneck regions being positioned upstream of and aligned with one heatexchanger of the first row of heat exchangers, and each neck region ofthe second plurality of neck regions being positioned upstream of andaligned with one heat exchanger of the second row of heat exchangers;wherein each heat exchanger is aligned with a neck region of the firstplurality of neck regions or the second plurality of neck regions andeach neck region is narrower than a frontal area of the heat exchangerwith which it is aligned such that the side curtains prevent turbulentflow from occurring as the bypass air enters the heat exchangers of thefirst row and the heat exchangers of the second row, and the sidecurtains reduce a difference in flow parameter between the bypass airand each heat exchanger; wherein the plurality of side curtains define aset of first passages in each of which the bypass air flows through oneof the neck regions of the first plurality of neck regions, then throughthe corresponding heat exchanger of the first row of heat exchangers,and subsequently through the corresponding second gap of the secondgaps; wherein the plurality of side curtains define a set of secondpassages in each of which the bypass air flows through one of the firstgaps and the corresponding neck region of the second plurality of neckregions, and subsequently through the corresponding heat exchanger ofthe second row of heat exchangers; and wherein each of the heatexchangers of the first row and each of the heat exchangers of thesecond row have a first portion with an intake and a second portion withan exhaust, and each of the plurality of side curtains is double walledto form a first pocket therewithin for receiving the intake or theexhaust of one of the heat exchangers of the first row and a secondpocket therewithin for receiving the intake or exhaust of one of theheat exchangers of the second row.
 12. The gas turbine engine of claim11, wherein the heat exchanger array is located in at least one of anupper bifurcation and a lower bifurcation of a nacelle of the gasturbine engine.
 13. The gas turbine engine of claim 11, Wherein the heatexchanger array is configured to receive bleed air from the compressorsection and configured to exhaust cooled bleed air for delivery to atleast one of the first turbine section and the second turbine section.14. The gas turbine engine of claim 11, wherein the heat exchanger arrayis configured to receive oil from a gearbox of the gas turbine engineand configured to exhaust cooled oil for delivery back to the gearbox.15. The gas turbine engine of claim 11, wherein the plurality of sidecurtains of the heat exchanger array are formed of a metallic orcomposite material.
 16. The gas turbine engine of claim 11, wherein eachof the side curtains of the plurality of side curtains forms a seal withone of the heat exchangers of the first row and one of the heatexchangers of the second row.
 17. The gas turbine engine of claim 11,wherein each of the first portions is covered by a first fairing andeach of the second portions is covered by a second fairing.
 18. The gasturbine engine of claim 17, wherein each of the first pockets receivesthe first fairing or the second fairing of the corresponding one of theheat exchangers of the first row and each of the second pockets receivesthe first fairing or the second fairing of the corresponding one of theheat exchangers of the second row.
 19. The gas turbine engine of claim11, wherein each of the heat exchangers in the heat exchanger array is ashell and tube heat exchanger, a plate fin heat exchanger, or a heatexchanger formed by additive manufacturing.